公开(公告)号：US06640547B2

公开(公告)日：2003-11-04

申请号：US10280173

申请日：2002-10-25

申请人： James H. Leahy, Jr.

发明人： James H. Leahy, Jr.

IPC分类号： F02C314

CPC分类号： F01D9/023 ,  F05D2260/202

摘要： An effusion cooled transition duct for transferring hot gases from a combustor to a turbine is disclosed. The transition duct includes a panel assembly with a generally cylindrical inlet end and a generally rectangular exit end with an increased first and second radius of curvature, a generally cylindrical inlet flange, and a generally rectangular end frame. Cooling of the transition duct is accomplished by a plurality of holes angled towards the end frame of the transition duct and drilled at an acute angle relative to the outer wall of the transition duct. The combination of the increase in radii of curvature of the panel assembly with the effusion cooling holes reduces component stresses and increases component life. An alternate embodiment of the present invention is shown which discloses shaped angled holes for improving the film cooling effectiveness of effusion holes on a transition duct while reducing film blow off.

摘要翻译： 公开了一种用于将热气体从燃烧器传送到涡轮机的渗出冷却的过渡管道。 过渡管道包括具有大致圆柱形的入口端和具有增加的第一和第二曲率半径的大致矩形出口端的面板组件，大致圆柱形的入口凸缘和大致矩形的端框架。 过渡管道的冷却通过与过渡管道的端部框架成角度的多个孔相对于过渡管道的外壁以锐角钻出。 面板组件的曲率半径的增加与渗出冷却孔的组合减少了部件应力并增加了部件的使用寿命。 示出了本发明的替代实施例，其中公开了用于在减少膜吹走的同时改善过渡管道上的渗出孔的膜冷却效果的成角度的孔。

公开(公告)号：US06634176B2

公开(公告)日：2003-10-21

申请号：US09977445

申请日：2001-10-15

申请人： Gregory C. Rouse ,  Octavio Solis ,  David Calta

发明人： Gregory C. Rouse ,  Octavio Solis ,  David Calta

IPC分类号： F02C314

CPC分类号： F01D25/30 ,  F02C7/10 ,  F05D2240/12

摘要： In a turbine engine with an annular recuperator surrounding the turbine, exhaust gas is directed from the turbine to the recuperator by a generally curved exhaust dome. A vortex disrupter structure extends from the exhaust dome to a point distal of the turbine to evenly distribute the exhaust gas entering the recuperator and sustain diffusion of the exhaust gas to increase the expansion ratio across the turbine.

摘要翻译： 在具有围绕涡轮机的环形换热器的涡轮发动机中，废气通过大致弯曲的排气拱顶从涡轮机引导到换热器。 涡流破坏器结构从排气拱顶延伸到涡轮机远端的一个点，以均匀分布进入换热器的排气并维持排气的扩散，从而增加涡轮机两端的膨胀比。

公开(公告)号：US06385959B1

公开(公告)日：2002-05-14

申请号：US09717603

申请日：2000-11-21

申请人： César Aguilera Montoya

发明人： César Aguilera Montoya

IPC分类号： F02C314

CPC分类号： F02C3/13 ,  F02C3/14 ,  F02C3/36 ,  F02K3/075 ,  F02K3/11

摘要： An engine having a casing and a compressor disposed within and rotatably coupled to the casing for generating pressurized gas. A primary combustion chamber disposed within the casing downstream of the compressor receives a primary portion of the gas generated by the compressor, and a secondary combustion chamber disposed within the casing downstream of the compressor receives a secondary portion of the gas generated by the compressor. Exhaust gases generated by the primary combustion chamber are applied to low and high pressure turbines located downstream of the primary combustion chamber. Exhaust gases generated by the secondary combustion chamber are only applied the low pressure turbine located downstream of the secondary combustion chamber.

摘要翻译： 具有外壳和压缩机的发动机，其设置在壳体内并可旋转地联接到壳体以产生加压气体。 设置在压缩机下游的壳体内的主燃烧室容纳由压缩机产生的气体的主要部分，并且设置在压缩机下游的壳体内的二次燃烧室接收由压缩机产生的气体的二次部分。 由主燃烧室产生的废气被施加到位于主燃烧室下游的低压和高压涡轮机。 二次燃烧室产生的废气只被施加在二次燃烧室下游的低压涡轮机。

公开(公告)号：US06260359B1

公开(公告)日：2001-07-17

申请号：US09431465

申请日：1999-11-01

申请人： Joseph D. Monty ,  John C. Jacobson

发明人： Joseph D. Monty ,  John C. Jacobson

IPC分类号： F02C314

CPC分类号： F23R3/06 ,  Y02T50/675

摘要： A combustor liner includes a row of primary dilution holes disposed aft of a forward end thereof, and a row of secondary dilution holes disposed between the primary holes and an aft end of the liner. The secondary holes vary in size circumferentially to a maximum size offset circumferentially from the primary holes.

摘要翻译： 燃烧器衬套包括一排在其前端后面设置的初级稀释孔，以及设置在主孔和衬套的后端之间的一排次级稀释孔。 二次孔的尺寸在周向上与从主孔周向偏移的最大尺寸变化。

公开(公告)号：US06662550B2

公开(公告)日：2003-12-16

申请号：US10131621

申请日：2002-04-25

申请人： Shmuel Eidelman ,  Dmitri Charov

发明人： Shmuel Eidelman ,  Dmitri Charov

IPC分类号： F02C314

CPC分类号： F02K7/04

摘要： A pulsed detonation engine having improved efficiency has a detonation chamber for receiving a detonable mixture, an igniter for igniting the detonable mixture, and an outlet for discharging detonation products. A diverging-converging nozzle is provided at the outlet of the detonation chamber. The geometry of the diverging-converging nozzle is selected to enable a relatively short nozzle to significantly improve efficiency of the pulsed detonation engine.

摘要翻译： 具有改进效率的脉冲爆震发动机具有用于接收可爆炸混合物的引爆室，用于点燃可爆炸混合物的点火器和用于排放爆震产物的出口。 在引爆室的出口处设有分流会聚喷嘴。 选择发散会聚喷嘴的几何形状以使得相对短的喷嘴能够显着提高脉冲爆震发动机的效率。

公开(公告)号：US06553767B2

公开(公告)日：2003-04-29

申请号：US09878836

申请日：2001-06-11

申请人： Gilbert Farmer ,  Daniel D. Brown ,  Myron E. Rutherford ,  Steven C. Vise ,  Jeffrey M. Martini

发明人： Gilbert Farmer ,  Daniel D. Brown ,  Myron E. Rutherford ,  Steven C. Vise ,  Jeffrey M. Martini

IPC分类号： F02C314

CPC分类号： F23R3/06 ,  F23R3/50 ,  Y02T50/675 ,  Y10T29/49346

摘要： An annular gas turbine engine combustor liner has a single piece annular shell circumscribed about a first axis of revolution. The shell has a hot side and a cold side, an annular dilution hole section, and a plurality of asymmetrical cylindrical dilution holes extending through the section. Pockets are circumferentially interdigitated between the dilution holes and extend into the shell from the cold side such that the pockets form dilution hole bosses between the pockets through which the dilution holes extend. Each of the dilution holes is circumscribed about a second axis of revolution which is not parallel to the first axis of revolution. The liner may further include forward and aft annular cooling nuggets located forward and aft of the dilution hole section and having annular film cooling slots which are open in the axially aftwardly direction. The shell is machined from a single piece integrally formed near net shape form such as a forging, a casting, or more particularly a spin or centrifugal casting. The invention includes a method for making the annular gas turbine engine combustor liner by forming a single piece integrally formed near net shape form and machining it to produce the shell and the above features in the shell.

公开(公告)号：US06298653B1

公开(公告)日：2001-10-09

申请号：US09522058

申请日：2000-03-09

申请人： Shawn P. Lawlor

发明人： Shawn P. Lawlor

IPC分类号： F02C314

CPC分类号： F01D1/34 ,  F02C3/14 ,  F02C3/16 ,  F02C7/04 ,  F02K1/827 ,  F02K7/005 ,  F05D2220/10 ,  F05D2220/34 ,  F05D2270/082 ,  Y02E20/16 ,  Y02T50/672 ,  Y02T50/677

摘要： A method of generating power. Ramjet structural components to provide inlet compression, a combustion chamber, and an outlet nozzle are provided at one or more circumferentially spaced locations along the periphery of a low aerodynamic drag rotor. Ramjet compression occurs by impingment of an inlet air stream between a rotating inlet structure and an adjacent stationary wall. The compressed air inlet stream provides oxygen for mixing with a fuel, such as natural gas, other suitable hydrocarbons, or hydrogen, which is supplied to the ramjet combustion chamber(s). Fuel is oxidized in the combustion chamber(s) to produce expanding combustion gases. Such gases escape out through a nozzle formed between a rotating outlet structure and a stationary wall. The ramjet operates at supersonic velocities, and preferably in excess of Mach 2.0, to produce shaft energy. The rotor rotates about an axis defined by an output shaft. The rotor acts as a structural member which transmits to the output shaft the thrust generated by the ramjets. Thermal and mechanical energy in escaping combustion gases may also be utilized to increase the overall efficiency of the ramjet engine.

摘要翻译： 发电的方法。 提供入口压缩的拉姆喷射结构部件，燃烧室和出口喷嘴沿着低空气动力学拖动转子的周边的一个或多个周向间隔的位置处设置。 通过在旋转的入口结构和相邻的固定壁之间撞击入口空气流而发生拉姆喷射压缩。 压缩空气入口流提供氧气，用于与供应到冲压喷气燃烧室的燃料（例如天然气，其它合适的烃或氢）混合。 燃料在燃烧室中被氧化以产生膨胀的燃烧气体。 这样的气体通过形成在旋转出口结构和固定壁之间的喷嘴逸出。 冲压式起重机以超音速运行，优选超过马赫数2.0，以产生轴能量。 转子围绕由输出轴限定的轴线旋转。 转子作为结构构件，其将输出轴传递到由冲击器产生的推力。 排出燃烧气体的热能和机械能也可用于提高冲压式喷气发动机的整体效率。

公开(公告)号：US06279309B1

公开(公告)日：2001-08-28

申请号：US09376157

申请日：1999-08-17

申请人： Shawn P. Lawlor ,  Kenneth H. Hicks, II

发明人： Shawn P. Lawlor ,  Kenneth H. Hicks, II

IPC分类号： F02C314

CPC分类号： F02K7/10 ,  F01D25/285

摘要： A modular power plant apparatus, and method of power plant assembly. An inlet air module is provided on feet which are mounted on self centering rugged linear roller guides which are linearly displaceable along a track. When the fuel-air mixing module is retracted along the roller track, the main engine housing is pivoted on an engine stand, to position the output shaft upward. An exhaust bearing plate is removable from the main rotor housing, to allow the rotating element to be removed. When exposed, hot section elements can be inspected, repaired, and replaced.

摘要翻译： 一种模块化发电厂装置及发电厂组装方法。 入口空气模块设置在脚上，其安装在沿着轨道线性移位的自对中凹凸线性滚子导轨上。 当燃料 - 空气混合模块沿着滚轮轨道缩回时，主发动机壳体在发动机支架上枢转，以将输出轴向上定位。 排气轴承板可从主转子壳体移除，以允许旋转元件被移除。 暴露时，可以检查，维修和更换热段元件。

公开(公告)号：US06758045B2

公开(公告)日：2004-07-06

申请号：US10233356

申请日：2002-08-30

申请人： Mina Dimov ,  Paul R. Angel ,  Steven Marakovits ,  Daniel Dale Brown

发明人： Mina Dimov ,  Paul R. Angel ,  Steven Marakovits ,  Daniel Dale Brown

IPC分类号： F02C314

CPC分类号： F23R3/002 ,  F23R3/346 ,  F23R3/50 ,  F23R2900/00005

摘要： A method enables a gas turbine engine multi-domed combustor including an outer liner and an inner liner that define a combustion chamber therebetween to be assembled. The method comprises coupling a first dome including a heat shield that includes an annular endbody that extends a first distance axially from the heat shield to the combustor outer liner, and coupling a second dome including a heat shield that includes an annular endbody that extends a second distance axially from the heat shield to the first dome, such that the second dome is radially aligned with respect to the first dome, and wherein the second dome second distance is less than the first dome first distance.

摘要翻译： 一种方法能够使燃气涡轮发动机多圆顶燃烧器包括在其间限定燃烧室以组装的外衬套和内衬套。 该方法包括联接包括隔热罩的第一穹顶，所述隔热罩包括环形端体，所述环形端体从所述隔热罩轴向延伸到所述燃烧器外衬套，并且连接包括隔热罩的第二穹顶，所述隔热罩包括环形端体， 从隔热板轴向延伸到第一圆顶，使得第二圆顶相对于第一圆顶径向对准，并且其中第二圆顶第二距离小于第一圆顶第一距离。

公开(公告)号：US06568187B1

公开(公告)日：2003-05-27

申请号：US09683290

申请日：2001-12-10

申请人： Stephen W. Jorgensen ,  James H. Leahy, Jr.

发明人： Stephen W. Jorgensen ,  James H. Leahy, Jr.

IPC分类号： F02C314

CPC分类号： F01D9/023 ,  F05D2260/202 ,  F23R2900/03041

摘要： An effusion cooled transition duct for transferring hot gases from a combustor to a turbine is disclosed. The transition duct includes a panel assembly with a generally cylindrical inlet end and a generally rectangular exit end with an increased first and second radius of curvature, a generally cylindrical inlet sleeve, and a generally rectangular end frame. Cooling of the transition duct is accomplished by a plurality of holes angled towards the end frame of the transition duct and drilled at an acute angle relative to the outer wall of the transition duct. Effusion cooling geometry, including coverage area, hole size, and surface angle will be optimized in the transition duct to tailor the temperature levels and gradients in order to minimize thermally induced stresses. The combination of the increase in radii of curvature of the panel assembly with the effusion cooling holes reduces component stresses and increases component life.

摘要翻译： 公开了一种用于将热气体从燃烧器传送到涡轮机的渗出冷却的过渡管道。 过渡管道包括具有大致圆柱形的入口端和具有增加的第一和第二曲率半径的大致矩形出口端的面板组件，大致圆柱形的入口套筒和大致矩形的端部框架。 过渡管道的冷却通过与过渡管道的端部框架成角度的多个孔相对于过渡管道的外壁以锐角钻出。 在过渡管道中将优化包括覆盖面积，孔尺寸和表面角度在内的流出冷却几何，以调整温度水平和梯度，以最小化热致应力。 面板组件的曲率半径的增加与渗出冷却孔的组合减少了部件应力并增加了部件的使用寿命。